AN AXISYMMETRIC NEAR WAKE ANALYSIS USING ROTATIONAL CHARACTERISTICS
POLYTECHNIC INST OF BROOKLYN FARMINGDALE NY DEPT OF AEROSPACE ENGINEERING AND APPLIED MECHANICS
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The near wake of a cone in a hypersonic stream is analyzed by simultaneously solving the inviscid region and the viscous shear layer. The inviscid region is solved by the use of rotational axisymmetric characteristics. It is assumed that viscosity and heat transfer play an important role only within a region bounded by streamlines which at the trailing edge of the cone are for the most part in the subsonic portion of the boundary layer. This region, termed the shear layer, lies between the dividing streamline or centerline and the basic streamline. The solution to the inviscid region is obtained by specifying conditions along the characteristic line originating at the shoulder of the cone, and by specifying the pressure distribution along a free surface basic streamline taken to be the streamline which at the shoulder of the cone separates the supersonic from the transonic and subsonic portions of the boundary layer. The pressure distribution along the basic streamline is iterated until the mass flow, momentum, and energy in the shear layer are consistent with the location of the dividing streamline and with the initial conditions at the edge of the cone. Profiles for pitot pressure, static pressure and stagnation enthalpy are presented and compared with experiments at different downstream locations. The shape and strength of both the lip and recompression shock are also shown. Both sets of results are seen to be in very good agreement with the experimental results available.
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